一种飞船用并联式太阳电池阵指向机构设计与分析  

Design and Analysis of a Parallel Pointing Mechanism for Spacecraft Solar Array

作　　者：李林[1] 丁健 孟庆平 王兴泽[1] 王秀丽 裴旭[2] 吴跃民[1] LI Lin;DING Jian;MENG Qingping;WANG Xingze;WANG Xiuli;PEI Xu;WU Yuemin(Beijing Institute of Spacecraft System Engineering,Beijing 100094,China;School of Mechanical Engineering and Automation,Beihang University,Beijing 100191,China)

机构地区：[1]北京空间飞行器总体设计部,北京100094 [2]北京航空航天大学机械工程及自动化学院,北京100191

出　　处：《载人航天》2018年第2期212-217,共6页Manned Spaceflight

摘　　要：为满足太阳电池阵在飞船上大范围指向要求,实现光照效率最大化,设计了一种用于飞船等航天器的新型并联式太阳电池阵指向机构,采用规则对称的模块化设计形式,具有工作空间大、可靠性高等特点。对新型并联式太阳电池阵指向机构进行了运动学正逆解计算,运用极限边界搜索法在MATLAB中计算了工作空间,建立了基于ADAMS的虚拟样机模型,并对其逆解进行了验证,以工程可实现性为原则,得出了多个逆解的筛选原则,为控制系统的参数筛选提供了依据。通过对并联机构的冗余特性进行分析,证明了在某一驱动组件卡死时,其仍具备较大的工作空间。该并联式指向机构还可用于航天器矢量推进器、天线指向等空间领域。A new type of parallel pointing mechanism was designed for the spacecraft solar array to meet its work space requirements so as to maximize the lighting efficiency.The mechanism adopted the modular design mode of regular symmetry.It had the characteristics of large working space and high reliability.The positive and inverse solutions were calculated,and the working space was cal-culated by the limit boundary searching method based on the MATLAB.A virtual prototype model was established based on ADAMS and the inverse solutions were verified.Based on the engineering realization principle,the selection principle of multiple inverse solutions was obtained which provid-ed the basis for the parameter selection of the control system.Finally,the redundancy characteristics of the parallel mechanism were analyzed.It is proved that when a drive assembly was jammed,the parallel pointing mechanism still had a larger working space.The parallel pointing mechanism could also be used in the field of spacecraft vector propeller,antenna pointing mechanism,etc.

关 键 词：飞船 并联指向机构 太阳电池阵 工作空间 冗余 

分 类 号：V19[航空宇航科学与技术—人机与环境工程]